EP2179141A2 - Machine thermodynamique - Google Patents

Machine thermodynamique

Info

Publication number
EP2179141A2
EP2179141A2 EP08801569A EP08801569A EP2179141A2 EP 2179141 A2 EP2179141 A2 EP 2179141A2 EP 08801569 A EP08801569 A EP 08801569A EP 08801569 A EP08801569 A EP 08801569A EP 2179141 A2 EP2179141 A2 EP 2179141A2
Authority
EP
European Patent Office
Prior art keywords
propellant gas
expansion
propellant
fuel
space
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP08801569A
Other languages
German (de)
English (en)
Other versions
EP2179141B1 (fr
Inventor
Harald Winkler
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Winkler Maschinen-Bau GmbH
Original Assignee
Individual
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Individual filed Critical Individual
Priority to EP08801569.8A priority Critical patent/EP2179141B1/fr
Publication of EP2179141A2 publication Critical patent/EP2179141A2/fr
Application granted granted Critical
Publication of EP2179141B1 publication Critical patent/EP2179141B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L7/00—Supplying non-combustible liquids or gases, other than air, to the fire, e.g. oxygen, steam
    • F23L7/002—Supplying water
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01B—MACHINES OR ENGINES, IN GENERAL OR OF POSITIVE-DISPLACEMENT TYPE, e.g. STEAM ENGINES
    • F01B9/00—Reciprocating-piston machines or engines characterised by connections between pistons and main shafts and not specific to preceding groups
    • F01B9/04—Reciprocating-piston machines or engines characterised by connections between pistons and main shafts and not specific to preceding groups with rotary main shaft other than crankshaft
    • F01B9/047—Reciprocating-piston machines or engines characterised by connections between pistons and main shafts and not specific to preceding groups with rotary main shaft other than crankshaft with rack and pinion
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01K—STEAM ENGINE PLANTS; STEAM ACCUMULATORS; ENGINE PLANTS NOT OTHERWISE PROVIDED FOR; ENGINES USING SPECIAL WORKING FLUIDS OR CYCLES
    • F01K21/00—Steam engine plants not otherwise provided for
    • F01K21/04—Steam engine plants not otherwise provided for using mixtures of steam and gas; Plants generating or heating steam by bringing water or steam into direct contact with hot gas
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F22—STEAM GENERATION
    • F22B—METHODS OF STEAM GENERATION; STEAM BOILERS
    • F22B1/00—Methods of steam generation characterised by form of heating method
    • F22B1/02—Methods of steam generation characterised by form of heating method by exploitation of the heat content of hot heat carriers
    • F22B1/18—Methods of steam generation characterised by form of heating method by exploitation of the heat content of hot heat carriers the heat carrier being a hot gas, e.g. waste gas such as exhaust gas of internal-combustion engines
    • F22B1/1853—Methods of steam generation characterised by form of heating method by exploitation of the heat content of hot heat carriers the heat carrier being a hot gas, e.g. waste gas such as exhaust gas of internal-combustion engines coming in direct contact with water in bulk or in sprays
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C6/00—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion
    • F23C6/04—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection
    • F23C6/045—Combustion apparatus characterised by the combination of two or more combustion chambers or combustion zones, e.g. for staged combustion in series connection with staged combustion in a single enclosure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/34—Burners specially adapted for use with means for pressurising the gaseous fuel or the combustion air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D91/00—Burners specially adapted for specific applications, not otherwise provided for
    • F23D91/02—Burners specially adapted for specific applications, not otherwise provided for for use in particular heating operations
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/03005—Burners with an internal combustion chamber, e.g. for obtaining an increased heat release, a high speed jet flame or being used for starting the combustion

Definitions

  • the present invention relates to a propellant gas generating device for generating a propellant gas under pressure for performing mechanical work and a method for operating such propellant gas generating device.
  • the present invention further relates to an expansion machine for converting an expansion of propellant gas under pressure into a mechanical movement, in particular into a rotary movement, and to a method for operating an expansion machine.
  • the invention relates to a heat engine for generating a mechanical movement using a fuel comprising a propellant gas generating device and an expansion engine, and a method for operating a heat engine.
  • the invention relates to a compressor for compressing a process gas, in particular air for use in a propellant gas generating device.
  • Heat engines are well known. Hereby, by burning a fuel, heat and a high-pressure propellant gas are basically generated. This propellant gas at high pressure is converted into a mechanical movement.
  • the mechanical efficiencies ie the ratio of mechanical energy contained in the mechanical movement, to the energy, the is contained by the combustion as heat and pressure in the propellant, is relatively poor and is usually below 50% or slightly above.
  • the object of the present invention is therefore to remedy the problems described as possible, or at least reduce.
  • the object of the present invention is to propose a heat engine which, in principle, enables better efficiency. At least an alternative machine should be presented.
  • a propellant gas generating device according to claim 1 is proposed.
  • Such a propellant gas generating device comprises amaschinegasdruckbenzol- ter for generating the propellant gas therein, and a combustion chamber for combusting a fuel for generating a fuel gas in which heat is generated by the combustion.
  • the fuel gas may then pass from the combustion chamber into the propellant pressure vessel, in addition to which secondary fuel, in particular water, is added to absorb the fuel gas heat.
  • secondary fuel liquid water, water vapor, compressed air or other suitable gas may be used.
  • this heat absorbs, which leads to an overall lowering of the temperature of the resulting propellant gas.
  • a cooling effect by a heat transfer from the fuel gas into the secondary fuel under Avoidance of energy dissipation.
  • the secondary fuel may also be referred to as a coolant, and the described process may be referred to as cooling, wherein cooling in the sense of heat removal from the system does not take place, but cooling by mixing.
  • the fuel gas together with the supplied secondary fuel then forms the propellant gas.
  • This propellant gas can then be forwarded, in particular while retaining a pressure, at least part of its pressure, from the propellant gas generating device for further use, namely conversion into mechanical movement.
  • the propellant gas generating device in particular the propellant gas pressure vessel, has at least one propellant gas outlet.
  • the secondary fuel is directly supplied to the fuel gas and mixed therewith.
  • the secondary fuel then forms a component of the propellant gas.
  • thermal energy is transferred from the fuel gas to the secondary fuel, whereby this thermal energy transferred to the secondary fuel is retained in the propellant, because the secondary fuel remains part of the propellant gas.
  • the combustion chamber is disposed in the propellant gas pressure vessel or forms part of the propellant gas pressure vessel.
  • the combustion chamber may be formed as a substantially closed space with corresponding combustion chamber walls, which is arranged in the LPG pressure vessel. The chamber outer walls are then in contact with an interior in the LPG pressure vessel. The combustion chamber then has an opening to the propellant pressure vessel interior, so that fuel gas can flow from the combustion chamber into the propellant gas pressure vessel. The heat of the combustion chamber can also be emitted via the chamber walls in the LPG pressure vessel.
  • the combustion chamber forms part of the propellant pressure vessel.
  • an interior of the combustion chamber is basically flowing into the interior of the propellant pressure vessel over.
  • the burner can be arranged, for example, at one end of a room and at a certain distance from the burner, the secondary fuel supply may be arranged. At an even further distance from the burner then an outlet opening for forwarding the propellant gas is arranged.
  • the combustion chamber basically flows into the propellant pressure vessel or its interior.
  • the combustion chamber with burner has a fuel supply for supplying the fuel and an air supply for supplying air.
  • air is to be understood in general as meaning, in particular, a substance which, together with the fuel after ignition, leads to the combustion or favors it. Air is an easily available variant.
  • pure oxygen or another suitable gas, especially oxygen could also be used.
  • the fuel used is preferably a liquid and / or gaseous fuel, such as gas, such as biogas, natural gas, oil and other oil products such as diesel, gasoline or kerosine, to name but a few examples.
  • Other examples of fuels are combustible suspensions, emulsions and coal dust.
  • the burner according to this embodiment is prepared to mix the air and the fuel, in particular to swirl and to realize starting of combustion in the combustion chamber.
  • the Treibgaser Wegungseinrich- device preferably uses compressed air, which is thus supplied under pressure to the burner and thus the combustion chamber.
  • a compressor or air compressor is used, which generates and provides such compressed air.
  • the air compressor may be part of the propellant gas generating device or the compressed air may be provided externally from a compressed air supply.
  • an air flow control valve is provided for controlling the pressure and / or controlling the amount of compressed air provided. As a result, the combustion process can be controlled by appropriate controlled addition of compressed air.
  • a fuel pump and / or a fuel compressor is provided to supply fuel to the combustion chamber and / or the burner, in particular under pressure.
  • a fuel quantity control valve is provided for controlling the amount of fuel to be supplied.
  • the fuel pump and / or the fuel compressor is connected to a fuel pressure accumulator to generate a pressure reservoir for the fuel.
  • a secondary fuel pump in particular a water pump is provided to provide the secondary fuel or water at the secondary fuel supply under pressure to initiate this under pressure in the LPG pressure vessel.
  • an optional water quantity control valve can be provided for controlling the amount of secondary fuel or water to be supplied. This also makes it possible to regulate the generation of the propellant gas better by controlling the amount of secondary fuel, in particular water, to be supplied, thereby controlling the process of propellant gas production and / or the composition of the propellant gas.
  • the burner and thus also the propellant pressure vessel work under atmospheric pressure. Accordingly, the supplied media must be supplied with at least this pressure.
  • a control unit for controlling the propellant gas generating device, in particular for controlling the fuel supply, the air supply and / or the secondary fuel supply.
  • a control unit which can also be referred to as a measuring, control and regulating unit, evaluates relevant inputs such as operator inputs and actual values and carries out corresponding controls by preferably giving corresponding control commands to actuating units.
  • Preferred input values are an operator input, in particular power specification as well as various measured values such as temperature values, for example in the combustion chamber and / or in the compressed gas tank, pressure values and a connected expansion machine, which converts the energy in the propellant into a rotational movement, a speed measurement.
  • a filling valve for supplying the propellant gas into the expansion machine as well as an outlet valve for discharging propellant gas from the expansion machine can be counted.
  • control unit in particular the numerical, measuring, control and regulating unit, is to calculate the best possible propellant gas generation on the basis of a basic program and in dependence of the variable inputs and to control these accordingly. In particular, it depends on the volume, pressure, temperature and environmental values.
  • a secondary fuel line is provided for guiding the secondary fuel to the secondary fuel supply, which runs along at least one wall of the propellant gas pressure vessel to achieve preheating of the secondary fuel by heat of the propellant gas pressure vessel.
  • the supply of secondary fuel in particular water, preferably has the purpose that cooling the fuel gas leads to heating of the secondary fuel and in particular to a volume expansion of the secondary fuel.
  • a strong volume expansion of the propellant gas is sought overall. It is not necessarily important that the secondary fuel is supplied as cold as possible to the LPG pressure vessel. On the contrary, it has proved to be favorable to cool the container walls in such a way that they do not suffer any thermal damage as far as possible.
  • the wall of themaschinegasdruck- container is thereby cooled and the secondary fuel, especially water, heated.
  • This heated secondary fuel, especially water can then be introduced into the propellant pressure vessel in the heated form so in the direction of flow of the water after the described secondary fuel lines.
  • the temperature may in this case preferably already be so high that the water is already vaporous, that is supplied as water vapor. This water can then accept thermal energy from the fuel gas and contribute to a volume and / or pressure increase of the propellant gas.
  • a further preferred embodiment provides that the propellant gas pressure vessel is designed at least in sections at least double-walled and between two walls of the secondary fuel and / or the air for feeding to the compressed gas tank or the combustion chamber is performed. It should be noted that in the propellant gas pressure vessel, in particular when the combustion chamber forms part of it, at different locations with different temperatures is to be expected. Due to its function, the highest temperature is to be expected in the area of the burner and thus the combustion chamber and it will decrease towards the propellant gas outlet. Thus, in the region of the combustion chamber, for example, a three-walledness can be provided.
  • a double walledness and, finally, a single-walledness to the propellant gas outlet can be provided, to name just one example.
  • the drewandtechnik can be used to lead in an area between two walls of air for supplying to the propellant pressure vessel or to the combustion chamber.
  • secondary water in particular water, can be conducted in another intermediate region and toward the two-walled region of the compressed gas container. After the location for supplying the secondary fuel can then be provided to the Treibgasauslass out a Einwandmaschine.
  • Another embodiment proposes a second secondary fuel supply for supplying a further secondary fuel.
  • compressed air may be provided as a first secondary fuel and water or water vapor as a second secondary fuel.
  • the secondary fuels are provided for feeding into the propellant gas pressure vessel.
  • secondary fuels are distinguished by a combustion air that enters the Combustion chamber is introduced to burn with the fuel.
  • the secondary fuels should not take part in the combustion, but should be initiated thereafter and achieve an increase in volume of the propellant gas.
  • the introduction of still further secondary fuels may be provided according to a further embodiment.
  • Another embodiment proposes a heat exchanger for heating at least one secondary fuel from heat of the propellant gas and / or from heat of another medium.
  • heating of the first, second and / or further secondary fuel is achieved, so that introduction of the relevant secondary fuel into the propellant pressure vessel in preheated state can be carried out in a simple manner.
  • heat of the propellant gas may be used by supplying propellant gas to the heat exchanger.
  • the propellant gas can be used, for example, after leaving an expansion machine connected downstream of the propellant gas generating device. It is also possible to use propellant gas which has left the propellant gas generator immediately or a combination. Further suitable for use in the heat exchanger other heat-carrying media, such as, for example, geothermally recovered gas.
  • a method according to claim 11 is proposed according to the invention.
  • This method is thus used to generate a propellant gas under pressure that can be used to perform mechanical work.
  • a propellant gas generating device which has a propellant pressure vessel, a combustion chamber and a secondary fuel supply.
  • the following steps are proposed, which are carried out essentially simultaneously, in particular continuously and thus in parallel.
  • a fuel is burned in the combustion chamber to generate a fuel gas.
  • This fuel gas has a high heat, as well as a certain overpressure, which is also due to the construction of a closed combustion chamber.
  • an open combustion chamber is also to be understood as an open combustion chamber arranged in a substantially closed propellant pressure vessel.
  • the fuel gas is directed into the LPG pressure vessel. This is done for example by a discharge of a generated propellant gas and the continued operation of the burner, so that fuel gas complies.
  • Secondary fuel in particular water, is introduced into the propellant pressure vessel and thus into the fuel gas. This leads to the cooling of the fuel gas and thereby to a heating of the secondary fuel, in particular of the water, and a consequent expansion of the secondary fuel or water.
  • the propellant gas is generated in the propellant gas pressure vessel, which has a correspondingly high pressure and can lead to a corresponding increase in volume of the propellant gas.
  • the secondary fuel is atomized and / or introduced as water vapor. As far as possible, the introduction is carried out so that the most favorable possible mixing of fuel gas and secondary fuel to the propellant takes place. Incidentally, the secondary fuel is supplied under pressure.
  • a propellant gas generating device is used in this method, as has already been explained above.
  • the propellant gas is generated so that the combustion takes place under pressure.
  • This is a characteristic of the burner and requires appropriate precautions, such as, in particular, the fuel and, as necessary, the pressurized air.
  • the secondary fuel is to be supplied to the pressurized gas container under pressure.
  • compressed air is supplied to the combustion chamber, which is provided by a compressed air compressor, wherein preferably a compressed air control valve is used and the pressure and / or the amount of compressed air is controlled. It is also favorable to supply fuel to the combustion chamber and / or the burner by means of a fuel pump and / or a fuel compressor, wherein preferably a fuel quantity regulating valve is used and the quantity of fuel to be supplied is controlled.
  • a control of the pressure, the temperature and / or the volume and / or mass flow of the supplied fuel is proposed for the control of the fuel quantity valve.
  • water is preferably supplied as a secondary fuel to the propellant pressure vessel by means of a water pump and optionally a water regulating valve is used, which supplies water under pressure and controls the amount of water supplied.
  • the control of the pressure and / or the amount of water can be carried out directly via the water pump.
  • the supply of a gaseous secondary fuel can be made similar to the supply of a gaseous fuel or the compressed air.
  • the process will be used as a flowable fuel, ie a liquid or gaseous fuel, such as, in particular, gas, oil, gasoline and diesel, to name but a few examples.
  • a flowable fuel ie a liquid or gaseous fuel, such as, in particular, gas, oil, gasoline and diesel, to name but a few examples.
  • preheated water can be used as secondary fuel and / or water can be misted into the propellant pressure vessel under pressure.
  • the heat extracted for preheating is retained in the system by supplying the thus preheated water to the fuel.
  • the method is preferably carried out in such a way that the hydrogen or secondary hydrogen supply, the fuel supply and / or the compressed air supply are dependent on measurements of conditions in the propellant gas generating device, in particular depending on measurements of the temperature, volume, pressure and / or or the composition of the propellant gas and / or depending on the temperature in the burner.
  • a control of the proportions and / or the pressure of the compressed air, the fuel and the water is performed.
  • the method is controlled such that the propellant gas leaves the propellant pressure vessel approximately at a pressure of 10 to 50 bar and a temperature in the range of 750 0 C to 1200 0 C. The higher the pressure, the higher the temperature and vice versa.
  • an expansion machine has a filling space and a propellant gas expansion space.
  • the moving body is arranged and guided in the filling space such that a pressure of the propellant gas, with which the filling space was filled, acts on the first pressure surface and thus pushes the moving body in a first direction and thus moves.
  • This movement can result from an expansion of the filled propellant gas or, in combination, it can take place together with the filling.
  • the moving body can be moved directly in the first direction.
  • the moving body is also guided into themaschinegasexpansionsraum, wherein the second pressure surface is oppositely directed Chryslergen the first pressure surface and an expansion of the devisgasexpansionsraum supplied propellant gas is moved to a movement of the moving body in the second direction opposite to the first direction.
  • the expansion machine is substantially prepared for movement of the moving body in the second direction due to expansion of the propellant gas in the propellant gas expansion space. The effect of the propellant gas in the filling space and the propellant gas expansion space are thus opposite.
  • the expansion machine is to be controlled accordingly so that a filling of the filling space and an expansion of the propellant gas in the expansion space successively, in particular takes place alternately.
  • the first pressure surface is smaller than the second pressure surface.
  • a higher pressure is required to exert the same force on the moving body as can be exerted in the propellant gas expansion space by a correspondingly lower propellant gas pressure.
  • the forces in the direction of the first and second movement direction are meant.
  • the filling space is formed as a cylinder space or annular gap and according to the first pressure surface is formed as a circular or annular surface, the moving body is designed as a piston and / or themaschinegasexpansionsraum is formed as an annular gap or cylinder space and the second pressure surface as Ring or circular surface is formed.
  • the use of a piston as a moving body is structurally simple to design.
  • the first expansion part arrangement can be designed as a whole simply and essentially cylindrically.
  • the filling space is an annular gap and the first pressure surface corresponding to an annular surface and themaschinegasexpansionsraum a cylinder chamber with the second pressure surface as a circular area. In this way it is also easy to realize that the first pressure surface is smaller than the second pressure surface.
  • the division may be reversed, a larger annular area than the circular area can be achieved with appropriate size distribution.
  • a common bore may be provided as a common cylinder space in which the movement body can move, in particular as a piston, and the filling space is then formed on one side of the piston and the propellant gas expansion space on the other side. Depending on the piston position, parts of the bore then belong to the filling space or to the propellant gas expansion space.
  • the expansion machine preferably comprises at least one filling valve functionally connected to the first filling space for introducing propellant gas into the first filling space, at least one outlet valve functionally connected to the propellant expansion space for discharging propellant gases from the propellant gas expansion space and / or at least one with the filling space and the propellant gas expansion space a functionally connected spill valve for opening and closing a connection between the fill space and the propellant gas expansion space to allow propellant gas to flow from the fill space to the propellant gas expansion space.
  • the filling space and the propellant gas expansion space are thus functionally connected via the at least one overflow valve.
  • this expander subassembly is therefore prepared so that a propellant gas flows via the filling valve into the filling space, where it leads to a movement of the moving body in the first direction, then flows via the overflow valve into the propellant gas expansion space, where it expands and causes the movement of the movement piston leads in the second direction and then - preferably after complete expansion and pressure decrease to atmospheric pressure - leaves themaschinegasexpansionsraum.
  • an expansion machine has an expansion sub-assembly with a dual function, which is particularly adapted to cooperate with a propellant gas generating device.
  • amaschinegasexpansionsraum is provided, which is to be filled with propellant gas and in which the propellant gas then expands to push the moving body in a first direction and to cause a corresponding translational movement ofndelskör- pers in this first direction.
  • This moving body is also guided in a compression space and has a compression surface to compress a process gas, in particular air, which may be used in the propellant gas generating device, to compress.
  • Compression is effected by a translational movement of the moving body in the first direction, so that a movement of the moving body caused by the expansion of the propellant gas leads to a compression of the process gas into the compression space.
  • the pressure surface is larger than the compression surface. In this way, on the one hand, it can be achieved that the same expansion pressure at the pressure surface can lead to a compression with a higher compression pressure on the side of the compression surface. On the other hand, it is achieved that the expansion of the propellant gas can achieve a movement of the moving body in the first direction with high energy or force and the compression of the process gas carried out thereby consumes little of this energy or force.
  • a common cylinder space or a common bore is preferably provided, in which the propellant gas expansion space and the compression space are formed.
  • the moving body then moves back and forth between the propellant gas expansion space and the compression space, in particular as a piston.
  • Suitable mediums are thermal oils, water, gases and other media.
  • a temperature compensation can also be provided in the range of cylinder heads and the medium used for heating to be used elsewhere.
  • two expansion sub-assemblies ie a first and a second are coupled together.
  • This coupling can be made both with an expansion part arrangement with filling space and fürgasexpansionsraum and with a expansion part arrangement with compression space and fürzasxpansionsraum.
  • the two expansion sub-assemblies are thus basically coupled in push-pull, so that an expansion of propellant gas in the Examgasexpansionsraum the first expansion sub-assembly leads to an emptying of the expanded propellant gas from themaschinegasexpansionsraum the second expansion sub-assembly.
  • the function of the filling spaces or the compression spaces remains accordingly preserved as they has already been explained in connection with in each case a single expansion part arrangement.
  • a flywheel for storing and delivering a kinetic energy from or to the moving body.
  • a flywheel can absorb kinetic energy, in particular, when the respectivemaschinegasexpansionsraum just expanding in the propellant, still small and the pressure of the propellant gas is still high.
  • An increasing expansion of the propellant gas and thus an enlargement of the propellant gas expansion space also leads to a decrease in the pressure of the propellant gas and corresponding to a decrease in the force of the moving body.
  • this movement can be maintained by the flywheel, even if a subsequent device takes mechanical energy.
  • the pressure of the propellant gas it is at least theoretically possible for the pressure of the propellant gas to drop to atmospheric pressure towards the end of the movement.
  • a conversion mechanism which has at least one toothed rack connected to the moving body and at least one toothed wheel means coupled to the toothed rack for converting a translational movement of the toothed rack into a rotatable toothed rack. Movement on the gear means.
  • This device has the advantage over a construction of wheel and connecting rod, that the rack basically always the same force is converted into the same torque, because by the use of the rack on the gear means permanently a force at a 90-degree angle of the translational movement direction to the radius at which the rack engages is achieved.
  • the expansion machine is characterized in that the conversion mechanism comprises at least a first gear means to convert a translational movement of a first direction of the moving body in a rotational movement with a first rotational direction and a second gear means to a translational movement of a second direction of the moving body in to turn a rotary motion with the first direction of rotation. It is therefore converted in each case a translational movement in a rotary motion with one and the same direction of rotation.
  • switching be effected between the first and second gear means in such a way that a movement of the moving body is converted into a rotational movement with the first, ie only one, direction of rotation.
  • each gear means preferably has a freewheel, in particular a controlled clutch freewheel, in order to be effective only in the first or the second direction of the translatory movement. Accordingly, according to a variant, no active switching needs to be carried out and a conversion to the said first rotary movement is always carried out. If a controlled coupling freewheel is used, it is possible to selectively deactivate the freewheel, so that a force can be transmitted from the gear means to the moving body even in the aforementioned direction of rotation. This can be advantageous if its movement is to be supported by the gear means to an end position of the moving body.
  • the moving body may be formed with two racks or a double rack by a rack or a portion of a double rack for each translational movement leads to a transfer.
  • the expansion machine control unit is prepared according to an embodiment to control the movement of a linear unit, in particular the piston and piston rod, via valve positions.
  • clutch freewheels can be controlled to suitably control a torque transmission.
  • the measurement and consideration of the state variables piston location, piston speed, piston movement direction, generated speed at an output shaft and valve positions and possibly states of the clutch freewheels are provided.
  • the expansion machine control unit can be prepared to coordinate these expansion machines in their movement.
  • a central control unit can be provided which, in addition to the tasks of the expansion machine control unit, also assumes control of a propellant gas generation unit.
  • a control unit for a propellant gas generation unit and an expansion machine control unit can be coordinated and / or combined in one unit.
  • an arrangement of at least two expansion machines is also proposed, wherein the expansion machines are coupled so that they each direct a torque to a common shaft, in particular the expansion machines are prepared to be operated synchronized and / or coordinated.
  • two expansion machines can be coupled via a conversion mechanism by, for example, each expansion machine with a rack on a conversion mechanism with two gear means engages.
  • two or more expansion machines transmit torque to a common shaft, wherein the expansion machines are arranged individually or in pairs in the axial direction of the common shaft one behind the other.
  • the expansion machines should be coupled in synchronism.
  • a method for operating an expansion machine with a first expansion part arrangement with a filling space and a propellant gas expansion space is also proposed. Accordingly, the following steps are performed: In the first step, the filling space is filled via at least one Guraumbetreibgas, wherein the pressure of the propellant gas acts on a first pressure surface on the moving body and presses in a first direction and thus moves in this direction. In the second step, the at least one filling valve is closed and then at least one overflow valve is opened, so that the propellant gas flows from the filling space into a propellant gas expansion space.
  • the opening of the at least one overflow valve can be carried out somewhat later than the closing of the at least one filling valve, ie later, in order to prevent a flow of propellant gas directly into the filling valve, and through the overflow valve.
  • a force acts on the second pressure surface on the moving body and is thus pressed and moved in a second direction.
  • the second direction is opposite to the first, so that the moving body moves back to step 1 again.
  • At least one exhaust valve in the propellant gas expansion chamber is opened to let the propellant gas escape from the propellant gas expansion chamber.
  • the pressure of the propellant gas is optimally equal to the surrounding, ie atmospheric pressure.
  • step 1 the method is repeated beginning with step 1, wherein the at least one outlet valve initially remains open.
  • step 1 the propellant gas expansion space is reduced again and the propellant gas contained can escape through the at least one opened outlet valve.
  • a method for operating an expansion machine with an expansion subassembly with a propellant gas expansion space and a compression space is also proposed.
  • the propellant gas expansion space is filled with propellant gas, so that the pressure of the propellant gas acts on a pressure surface on a moving body and thereby moves the moving body in a first direction.
  • This movement in the first direction reduces the compression space and compresses the process gas contained therein.
  • the compressed process gas can be supplied subsequently or already during compression of its use.
  • the moving body is moved back in the second direction, wherein themaschinegasexpansionsraum is emptied due to at least one open exhaust valve.
  • the return movement of the moving body can be achieved for example by a flywheel or other force not caused by this first expansion part arrangement.
  • the compression chamber is filled with process gas. In the simplest case, this may mean that an inlet valve is opened in the compression space and air flows into the compression space by the movement of the moving body back.
  • step 1 is repeated, wherein in any case before the described inlet valve has been closed in the compression chamber, so that a desired compression pressure for the process gas can build up.
  • two expansion sub-assemblies are operated coupled with the same characteristics.
  • the same features do not necessarily mean that the expansion sub-assemblies are completely identical, but that they have the same structure in principle, in particular two expansion sub-assemblies are operated coupled with one charge space and each coupled to a propellant expansion space, or two expansion sub-assemblies each having a propellant gas expansion space and a compression space operated together.
  • the directions of movement are in this case set opposite, the movements complement each other by the two expansion sub-assemblies have a common moving body.
  • the two expansion subassemblies are Accordingly, operated so that they move the moving body in each case in the same direction, so that the filling and emptying of the Examgasexpansions- space of the first expansion sub-assembly is always reversed for filling and emptying of the propellant gas expansion space of the second expansion sub-assembly.
  • a heat engine for generating a mechanical movement using a fuel which comprises a propellant gas generating means according to the invention for generating a propellant gas and an expansion machine according to the invention for converting an expansion of propellant under pressure into a mechanical movement, in particular rotational movement, wherein the propellant gas generating means and Expansion machine are coupled together so that the propellant gas generated by the propellant gas generating means is supplied to the expansion machine, in particular at least one filling valve or inlet valve in akulturgasexpansionshunt is provided.
  • the propellant gas generating means and the expansion machine are matched.
  • the propellant gas generating device essentially supplies a propellant gas with as constant as possible values such as constant pressure and temperature.
  • the expansion machine is prepared to be operated substantially with a propellant gas at a constant pressure.
  • the two devices thus complement each other favorably to the heat engine.
  • an expansion machine is used with at least one expansion space, preferably two expansion spaces.
  • the expansion machine can be operated with the propellant gas provided by the propellant gas generating device and at the same time compress a process gas and be available as compressed gas, in particular compressed air of the propellant gas generating device, in particular the burner. This results in particularly good synergy effects.
  • a method for operating a heat engine according to claim 40 is proposed.
  • a compressor for compressing a process gas, in particular air, according to claim 41 is proposed.
  • Such a compressor has a first and a second compression space, each having a first and second compression body. In this case, a coupling of the two compression spaces takes place in that the second compression space is formed in the first compression body.
  • the first compression space is prepared to compress the process gas in a first compression stage to a volume having a first compression pressure.
  • a corresponding connecting valve or more is provided in order to then transfer the compressed process gas into the second compression space. After compression in the first compression stage, the process gas thus flows into the second compression space.
  • the second compression space is then prepared to further compress the process gas in a second compression stage, correspondingly reducing the volume and increasing the compression pressure.
  • the first compression space and the second compression body are fixedly arranged relative to one another and the first compression body is movably arranged in two directions relative to the first compression space and the second compression body such that its movement either reduces the first compression space or increases the second or vice versa
  • the first compression space forms a cylinder, in which the first compression body is also guided in a cylindrical manner.
  • the first compression body of the second compression space is also arranged as a cylinder - corresponding to a smaller diameter.
  • the second compression body is finally performed in this second compression space also as a corresponding cylinder with a smaller diameter. For compressing the process gas this is now first admitted into the first compression space, which is expanded here.
  • the first compression body then moves - after the corresponding valves were closed - so in the first compression space that this reduced and the process gas is compressed. Since the first compression space and the second compression body are each fixed, automatically increases the second compression space by the movement of the first compression body. However, due to the smaller cylinder diameter, this second compression space is relatively small and the process gas compressed in the first compression stage can now be introduced into this second compression space without this losing its compression again. In this case, due to the small second compression space, the connecting valve between the first and second compression space may be open during the first compression stage. In this first compression stage, although the second compression space is increased while the first is being reduced in size, it is still small in comparison with the large compression space and the available volume for the process gas is also reduced with the connection valve open. For the second compression stage, however, the connection valve must be closed, so that when weighing back the first compression body, whereby the second compression space is reduced, the process gas does not flow back into the first compression space.
  • the connecting valve may be provided as a check valve, which allows only a flow from the first to the second compression chamber.
  • an inlet valve may be formed from the outside to the first compression chamber as a check valve.
  • a further embodiment proposes to mechanically couple a compressor, that is to say in particular a described compressor, which in principle is structurally independent of an expansion machine, with an expansion machine in order to use a force generated by the expansion machine for operating the compressor.
  • Chen compressor to set up a conversion mechanism, in particular to connect with a gear means of the conversion mechanism, so as to operate the compressor.
  • a steam generator is also proposed for generating water vapor from water comprising:
  • the steam generator is prepared to inject preheated water from the preheat area via propellant injection nozzles into the evaporation area so that the water in the evaporation area evaporates to water vapor
  • the heat source preferably being prepared to supply and / or generate a heating medium which is first to evaporate - Is passed area to heat it and from there to the preheating area is heated to this.
  • the first expansion space may also be referred to as Treibgas sleepllraum and the second expansion space may also be referred to asmaschinegasexpansionsraum.
  • Fuel and / or fuel can also be referred to as fuel, but differs in function from the secondary fuel. Fuel, fuel and fuel are to be differentiated in the importance of secondary fuel.
  • Propellant pressure vessel may also be referred to as Treibgasreaktordruck admirer.
  • a control unit usually comprises a measuring, control and regulating unit.
  • a pressure surface can form a partial area of a total area, the pressure bearing on the entire area, but only effective on the pressure area.
  • the term pressure area refers to the area at which the pressure is effective.
  • Fig. 1 shows a propellant gas generating device with two LPG pressure vessels according to an embodiment of the invention.
  • Fig. 2 shows an expansion machine according to an embodiment of the invention in an operating position.
  • FIG. 3 to 5 show an expansion machine according to FIG. 2 in further operating positions.
  • Fig. 6A shows a propellant gas generating device according to Fig. 1, and an expansion machine according to the figures 2 to 5, which are coupled.
  • Fig. 6B shows a heat engine according to Figure 6Aa, but with a changed operating position of the expansion machine.
  • Fig. 7 shows a propellant gas reactor according to another embodiment of the Invention.
  • Fig. 8 shows a propellant gas reactor according to another embodiment of the invention.
  • Fig. 9 illustrates the structure and operation of an expansion machine according to another embodiment of the invention.
  • 10 to 12 show a heat engine according to an embodiment with two propellant gas reactors and an expansion machine in a schematic representation and in different operating states.
  • Fig. 13 shows a heat engine with propellant gas reactors and an expansion machine, which is connected via its conversion mechanism with a compressor according to an embodiment.
  • Fig. 14 shows a conversion mechanism which is coupled with two toothed piston rods in a perspective view.
  • FIG. 15 schematically illustrates the force and torque effects of the arrangement shown in FIG.
  • Fig. 16 shows a further embodiment of a heat engine schematically.
  • Fig. 17 shows a section of an expansion machine according to another embodiment.
  • Fig. 18 shows a piston of an expansion machine according to another embodiment.
  • Fig. 19 shows a cross section through an insulated cylinder of an expansion machine to illustrate the structure.
  • Fig. 20 shows a steam generator for generating water vapor from water according to the present invention.
  • Fig. 21 shows a further embodiment of an expansion machine in a side view.
  • Fig. 22 shows an expansion machine according to the figure 21 in a plan view.
  • propellant gas generating device One aspect of the invention is the propellant gas generating device.
  • suitable propellant gas production can be accomplished in a variety of ways. Depending on the selected energy source (fuel), the appropriate technology should be chosen. For solid fuels such as coal, wood, etc., e.g. Commercially available steam boiler systems in question. For liquid fuels such as oil, or gaseous fuels such as landfill gas, biogas, natural gas, etc., the propellant gas generating device according to the invention can be used.
  • the energy conversion from the energy source to the propellant gas should have an efficiency ⁇ > 90%.
  • the temperature of the propellant gas should be at least controllable so that it causes no thermal damage in the expansion machine.
  • the pressure of the propellant gas should be adjustable.
  • the volume of the propellant gas should be adjustable.
  • the propellant gas generating device 2 according to FIG. 1 has two propellant gas pressure vessels 4, which are of basically the same design and, incidentally, can also be referred to as propellant gas reactor pressure vessels.
  • the task The propellant gas pressure vessel 4 is to produce propellant gas suitable by reacting air, fuel and preheated water, so that it is able to perform mechanical work.
  • each of the two propellant gas pressure vessel 4 a combustion chamber 6, each with a burner 8 is arranged to burn fuel.
  • the task of the combustion chamber 6 is to ensure the best possible combustion of a fuel-air mixture.
  • the propellant gas pressure vessel with the combustion chamber 6 forms a propellant gas reactor 5.
  • Each burner 8 is intended to start and ensure optimum combustion by turbulence of air, fuel and their ignition.
  • the propellant gas generating device 2 comprises a central measuring, control and regulating unit 10, also referred to as MSRe or MSR 10 for short.
  • MSR 10 central measuring, control and regulating unit 10 for short.
  • Variable inputs to this MSR 10 are an input for a performance target 12 that allows a user to specify power via operator commands, and at least one input for a temperature reading 14, an input for a pressure reading 16, and an input for a speed reading of a propellant generator Mechanics.
  • the measured values of the temperature and the pressure relate to the temperature and the pressure of the propellant gas, in particular to an outlet 18 of the propellant gas pressure vessel 4.
  • the MSR outputs 10 control commands as outputs. These include an air control output 20 for outputting a drive command to at least one air pressure control valve 22 to control an air supply to the burner 8, a fuel control output 24 for outputting a drive command to at least one fuel control valve 26 to control a fuel supply, and a water control output 28 for outputting a drive command at least one water quantity control valve 30 to control the supply of an amount of water to propellant pressure vessel. Further, the MSR 10 has a charge control output 32 for outputting a drive command to control a charge gas supply amount for a downstream expansion engine, and a charge control output 34 for outputting a drive command for a downstream expansion engine to have an exhaust valve for discharging the propellant gas To control expansion machine.
  • the MSR 10 is intended, based on a program and depending on the above-mentioned inputs, to calculate the best possible generation of propellant gas and to control it by means of corresponding control commands.
  • an air compressor 36 is provided, which provides by means of a memory in front of the air pressure control valve 22, an air pressure which is at least 43 bar in one embodiment.
  • the compressor 36 is driven by a linear linkage from the expander to ensure proportional production of compressed air.
  • the compressor 36 provides compressed air and task of the air pressure control valve 22 is to supply according to a specification by the central MSR 10 the combustion chambers 6 of the propellant 5, an optimal amount of air.
  • a fuel pump 38 is provided to ensure a fuel pressure by means of a reservoir upstream of the fuel control valve 26. This
  • Fuel pressure in the present embodiment is about 200 bar when using a liquid fuel.
  • Fuel quantity control valve is referred to, according to the above-described specifications of the MSR 10 to the combustion chambers 6 of the propellant gas reactors 5 supply the most optimal amounts of fuel.
  • the combustion chambers 6 at least one injection nozzle 40.
  • the water flow control valve 30 is to provide for a regulated supply of water to the LPG pressure vessels. This supply takes place in accordance with a specification of the MSR 10, the water being supplied to nebulization nozzles 44 in the propellant gas pressure containers 4 of the propellant gas reactors 5, which are each arranged in the region of a container wall 46. In this case, optimal amounts of water preheated water to be supplied in order to achieve a temperature and volume optimization of the propellant gas. For the supply of water from the water flow control valve 30 to the nebulizer corresponding water supply lines 48 are provided.
  • the propellant gas reactor 5 operates with a non-atmospheric combustion technique, that is, the combustion takes place under overpressure. Propellant gas from fuel, air and water is generated in the propellant gas reactor 5.
  • the special task of the propellant gas reactor 5 is to generate propellant gas with the largest possible volume and moderate temperature.
  • moderate temperature is meant a temperature range that does not damage the machine designs of the
  • Propellant reactor pressure vessel 6 and an expansion machine causes the generated propellant gas is supplied.
  • Controlled and controlled by the MSR 10 is supplied via the air compressor 36, which can also be referred to as a compressed air generator, and the air flow control valve 22, and a line comprising the air lines 35 compressed air to a burner 8 comprehensive burner system within the combustion chamber 6 in the propellant reactor pressure vessel 4.
  • the air compressor 36 which can also be referred to as a compressed air generator, and the air flow control valve 22, and a line comprising the air lines 35 compressed air to a burner 8 comprehensive burner system within the combustion chamber 6 in the propellant reactor pressure vessel 4.
  • the task of the combustion chamber 6 is to provide the combustion process a sufficient shelter in which the combustion as optimal as possible, that is, at the highest possible temperatures and the necessary residence, as completely as possible can take place to allow the most clean fuel gas.
  • Positive features here are that an optimally optimized combustion time window can be achieved and possibilities for optimal fuel combustion are created, in order to minimize any particulate matter risk and to obtain as little NO x as possible.
  • This process is also controlled and controlled by the MSR, wherein the pressurized water has previously passed through the water pump 42, the water reservoir and the water flow control valve 30.
  • the water has optionally pass through a heat exchanger of the compressed air generator or air compressor 36, wherein it heats up strongly.
  • the MSR 10 system measures, controls and controls the previously described supply of Fuel gas and water so that the largest possible propellant gas volume is formed in a temperature range, which does not damage the propellant gas reactor pressure vessel 4 and a downstream expansion machine thermally.
  • the task of the propellant gas reactor pressure vessel 4 is to concentrate the propellant gases formed in it and possibly to supply the downstream expansion machine via a pipeline system, and to withstand the expected pressure resulting from the dynamic pressure of the expansion machine.
  • Another task of the MSRe system is to continuously measure and regulate the proportions of compressed air, fuel and water as a function of pressure, volume and temperature of the propellant gas during the operation of the WWKM.
  • a particular advantage of the propellant gas reactor system ie the propellant gas reactor 5 with associated components including the MSR 10, is that, due to the system, a direct, intimate temperature-volume conversion takes place. That is, by mixing, a volume increase is achieved directly in the same room. Efficiency losses due to temperature - volume separating solid walls such as e.g. Pipelines for boiler plants are not available.
  • Figure 1 is a schematic representation showing two propellant gas reactors 5 in a sectional view similar to a sectional view in the basic structure, which does not represent exact size ratios.
  • the MSR 10 and other elements between the two LPG 5 are shown. In this arrangement, but it does not matter and in particular the MSR 10 can be arranged at basically any position.
  • an expansion machine 202 according to an embodiment of the invention is explained, wherein the expansion machine 202 is illustrated for explaining the individual elements in an operating position. For the representation a partial sectional view was chosen.
  • the expansion machine 202 has two cylinders 204 - according to the figure 2, a right cylinder and a left cylinder - in which propellant gas can expand at a corresponding operating position.
  • Each cylinder has a cylinder head 206 with a plurality of exhaust valves 208 through which propellant gas may flow in the open state.
  • the exhaust valves 208 in the right cylinder 204 are shown in the open and the left cylinder in the closed state.
  • annular channel 210 For filling each cylinder 204 with propellant gas an annular channel 210 is provided with filling valves 212 each.
  • the right-hand cylinder 204 has a closed filling valve 212 and the left-hand cylinder 204 an open filling valve 212.
  • propellant gas can thus be provided on the annular channel 210 and flow into the cylinder 204 through the at least one filling valve 212 shown on the right.
  • a piston 214 is guided by means of a respective annular cylinder guide 216 in a cylindrical inner space or a cylindrical bore to allow axial movement of the piston 214.
  • the cylinder guide 216 is disposed in and on the cylinder 204 and also ensures a seal of the piston 214 against the cylinder 204.
  • At each Piston 214 is also an annular piston seal 218 arranged, which seals the piston against the cylinder 204 and reaches a guide.
  • the piston 214 has a piston body 220 and a Kolbenstimwand 222, which are each firmly connected to each other, said connection of the piston body 220 is not shown with the piston end wall 222 in the figure 2.
  • Each cylinder 204 has a propellant gas space 224.
  • Themaschinegas Stahlraum 224 is formed between the piston body 220, the piston end wall 222 and the cylinder 204 and varies with the position of the respective piston 214.
  • the propellant gas space 224 shown in the right cylinder 204 is thus composed of a cylindrical portion and an annular gap.
  • the Treibgas colllraum 224 is connected via a plurality fürströmventile 226 with amaschinegasexpansionsraum 228.
  • the propellant gas expansion space 228 changes with the position of the piston 214 and has its largest extent in the right cylinder 204 and its smallest extent in the case of the left cylinder 204.
  • the overflow valves 226 in the right cylinder 204 are closed and the left cylinder 204 shown open. With the spill valves 226 open, propellant gas may flow from the propellant gas fill space 224 into the respective propellant gas expansion space 228.
  • Both pistons 214 are fixedly connected to each other via a common piston rod 230.
  • the piston rod 230 is toothed on both sides to engage in two sprockets 232 to convert a force of the piston 214 in a torque.
  • Each ring gear 232 is connected to a freewheel 234, so that in each case only in one direction of rotation a torque is transmitted to the freewheel 234 connected to the hub 236.
  • Arrows indicate a direction of rotation 238 into which a torque is transmitted.
  • Both freewheels 234 are selected so that a torque is always transmitted in the direction of this direction of rotation 238 of a respective ring gear 232 to the corresponding hub 236.
  • the hubs have sprocket teeth and are over a Chain drive 240 connected to each other to achieve a synchronization of the torque.
  • An oscillating movement of the piston rod 230 can thus always be converted via the choice of the freewheel 234 into a torque with the direction of rotation 238.
  • the torque thus generated can be removed via output shafts 242 and fed to a further use.
  • propellant gas pressure volume coming from a propellant gas reactor and controlled by an MSR is indicated at all annular channels 10 of the expansion machine 202.
  • the stroke direction is directed to the right as shown in FIG.
  • the spill valves 226, fill valves 212 and exhaust valves 208 are regularly controlled.
  • the pistons 214 and piston rod 230 have arrived at a left inner direction reversal point, ie if the piston end wall 222 has arrived at approximately the filling valve 212 in the right cylinder 204, close the overflow valves 226 in the right cylinder 204, open the filling valves 212 in the right annular channel 210, as well the exhaust valves 208 in the right cylinder head 206 and release a substantially expansionslose propellant charge the rightmaschinegas Struktures 224.
  • open - also controlled regularly - the overflow 226 in the left piston 214 and thus open up an expansion process of the left previously filledmaschinegas Strukturllraums 224th
  • both pistons 214 expose their thrust and expansion forces adding to each other to the right.
  • the fill valves 212 are closed again when the right hand fill space 224 is filled and the piston 214 has reached its extreme right position.
  • the effective piston area is the size of the circular area of the end face of the piston body 220.
  • the expansion forces acting on the left-hand piston 214 are initially very high due to the falling pressure curve, that is, the decreasing pressure, the maximum pressure approximately corresponding to the filling pressure, and possibly decreasing to zero when the pressure is up to reduced atmospheric pressure. In this case, there are no energy drains due to unused escaping residual pressure.
  • Figure 3 shows the expansion machine shortly before reaching the right inner direction reversal point, so shortly before in the left cylinder 204, the piston end wall 222 has reached the filling valve 212.
  • the MSR gives the right exhaust valves 208 the closing command, as a result of which a residual propellant gas cushion builds up, absorbing the kinetic energy from the moving linear unit, namely the piston 214 and the piston rod 230, decelerating it to speed 0 and immediately accelerated linearly again in the other direction.
  • the expansion machine 202 is shown in an operating position at the stroke is left.
  • the left overflow valves 226 close, open the filling valves 212 in the left annular channel 210, and the exhaust valves 208 in the left cylinder head 206 and release the propellant gas filling of the propellant gas filling space 224 without expansion.
  • the overflow valves 226 in the right-hand piston 214 which is shown in FIG. 4, likewise open at regular intervals, thereby opening up the expansion process of the right-hand previously filled propellant charge space 224.
  • both pistons 214 unfold their thrust and expansion forces mutually adding to the left.
  • the thrust forces on the annular surface of the left piston - resulting from themaschinegas Stahlstoffmaschinell horrin times the effective annular surface - are consistent.
  • the forces acting on the right piston 214 expansion forces are initially very large due to the falling pressure curve, in which case the maximum pressure corresponds approximately to the filling pressure and can be reduced to ambient pressure with complete expansion. A positive torque input of approx. 96% is aimed for. If the expansion pressure builds up to ambient pressure, there are no energy outflows due to unused escaping residual pressure.
  • the MSR Shortly before reaching the left inner direction reversal point, as shown in FIG. 5, the MSR outputs the left exhaust valve 208
  • Closing command as a result of a Resttreibgaspolster builds up the kinetic energy from the moving linear unit consisting of the
  • Piston 214 and the piston rod 230 receives this while on
  • the linear cycle described so far with reference to FIGS. 2 to 5 is at its starting point and begins a new linear cycle with the same sequence.
  • the thermodynamic energy previously generated or converted in the propellant gas reactor is converted into a linear mechanical energy.
  • the double-toothed piston rod 230 has a toothing, which - according to Figure 2 - above and below with a ring gear 232 is engaged. If the piston rod 230 moves to the right, this results in the upper one
  • Gear ring 232 a left-turning torque and the lower ring gear 232 a right-turning torque. If the piston rod 230 moves to the left, a right-turning torque is produced in the upper ring gear 232 and a left-turning torque in the lower ring gear 232.
  • the freewheels 234 are arranged between both sprockets 232 and the wheel hubs 236, which have corresponding sprocket toothings.
  • the purpose of the freewheels 234 is to transmit the torques, which are each shown turning to the left, onto the wheel hubs 236, or not to transmit the respectively right-rotating torques to the wheel hubs 236.
  • the tasks of the wheel hubs 236 torque-connected and radially, and axially mounted drive shafts are to couple the generated torques - the generated powers of the expansion machine with other elements, or to forward to a power consumers on.
  • the chain drive 240 is provided for synchronizing the torques on both hubs, the task of which is to synchronize both output shafts 242 in a torque-proof manner and moreover a torque or power transfer of the total power optionally at both output shafts 242 to enable.
  • FIGS. 2 to 5 schematically represent the same expansion machine 202, even if some deviations in size should possibly be present in the illustration. Figures 2 to 5 differ in the operating states shown in each case.
  • FIG. 6A illustrates the interaction of the propellant gas generating device 2 with an expansion machine 202 coupled thereto.
  • the propellant gas generating device 2 generates propellant gas in the two propellant gas reactors 5.
  • the propellant gas reactors 5 are coupled with their propellant pressure vessels 4 to the cylinders 204 of the expansion machine 202 so that propellant gas from the outlet 18 the propellant pressure vessel is supplied to the annular channels 210 and is thus provided to the filling valves 212.
  • the MSR 10 is provided for simultaneously controlling the propellant gas reactors 5 and the expansion engine 202.
  • measured values from the propellant gas reactors 5 and the expansion machine 202 can be taken into account.
  • a reading may be the pressure in the propellant gas space 224.
  • the direction of movement of the linear unit consisting of the piston 214 and the piston rod 230 is directed to the right as shown and leads to a force and torque transmission over the upper ring gear 232 and the direction of rotation is directed to the left.
  • FIG. 6B the direction of movement of the linear unit is directed to the left as shown and results in a transmission of force and torque via the lower ring gear 232 and the direction of rotation is also directed to the left.
  • the torque at the wheel hubs 236 is directed to the left.
  • the two sprockets 232 rotate opposite and with changing direction.
  • the propellant gas reactor 705 of FIG. 7 has a combustion chamber 706 with a burner 708. In the area of the burner 708, fuel is supplied to the combustion chamber 706 via injection nozzles 740 and combustion air via air inlets or air nozzles 737. In this case, the fuel is supplied via fuel lines 739 and the combustion air via air lines 735.
  • compressed air supply lines 750 In the vicinity of the combustion chamber 706, further compressed air is supplied via compressed air supply lines 750. This additional compressed air is provided via compressed air lines 752. This additional compressed air can also be referred to as secondary fuel, which lowers the temperature of the propellant gas and increases its volume.
  • a portion of the compressed air supply lines 752 extends directly outside the combustion chamber 706 and thereby forms a second wall for the combustion chamber 706.
  • the combustion chamber 706 thermally insulated to the outside, which on the other hand leads to a heating of the supplied in this double wall further compressed air.
  • the compressed air is thus heated prior to feeding in the area of the compressed air supply lines 750 in order to favor the process in the propellant gas reactor 705.
  • the propellant gas reactor 705 is supplied with water and / or steam via feeds 749 under pressure.
  • the feeders 749 are still arranged above the compressed air supply lines 750 according to FIG.
  • the water should act substantially thermally in the generated propellant, but not act directly on the combustion process in the combustor 706.
  • part of the supply lines 748 are guided outside the combustion chamber 706 within an insulation wall 745, so that a further double walling arises, which increases the insulation of the propellant gas reactor 705 to the outside and at the same time leads to a heating of the water or water vapor in the supply lines 748.
  • the water or steam is thus heated to the propellant gas reactor 705 is supplied.
  • the supply of water vapor leads to an increase in volume of the propellant gas while reducing temperature and the water or Steam can thus also be referred to as another secondary fuel.
  • the term water may also mean water vapor.
  • combustion is thus effected by supplying fuel via the injection nozzles 740 and combustion air via the air nozzles 737, which combustion can still be assisted by supplying additional compressed air in the area of the compressed air supply lines 750.
  • a hot propellant gas is generated at a higher pressure and lower temperature.
  • a further increase in volume and temperature reduction is achieved by supplying the water in the area of the water supply 749.
  • the propellant gas thus produced can finally exit the propellant gas reactor 705 through the outlet 718 and be supplied to a further connection, in particular an expansion machine.
  • the propellant gas reactor 805 of FIG. 8 has a propellant pressure vessel 804, the interior 803 of which immediately adjoins a combustion chamber 806. In the combustion chamber 806 is in the region of a burner 808 via a
  • Combustion air is also introduced into the combustion chamber 806 via air nozzles 837. After ignition, the fuel with the combustion air burns to a fuel gas in the combustion chamber 806 and passes from there into the propellant pressure vessel 804.
  • the combustion chamber 806 and the inner space 803 are substantially surrounded by a heat-resistant wall 860.
  • a first secondary fuel is supplied via a first secondary fuel passage 851.
  • the secondary fuel passage 851 opens into first secondary fuel feeds 850 formed in the heat-resistant wall 860, which allow the supply of the first secondary fuel into the propellant pressure vessel interior 803.
  • the combustion process is already complete or at least substantially complete.
  • the mixing of the first secondary fuel with the fuel gas leads to an increase in volume of the resulting propellant gas.
  • the first secondary fuel absorbs heat from the fuel gas.
  • the first secondary fuel passage 851 is bounded outwardly by a heat-resistant center wall 862. Outside this heat-resistant middle wall 862, a second secondary fuel channel 871 is arranged, which provides a second secondary fuel to the interior 803 of the propellant pressure vessel 804 and thus of the propellant gas reactor 805. According to the propellant gas reactor 805 of FIG. 8, it is provided to supply compressed air as the first secondary fuel and to supply water vapor as the second secondary fuel.
  • the second secondary fuel passage 871 opens into second secondary fuel feeds 870, which may introduce the second secondary fuel into the interior 803.
  • the second secondary fuel is supplied to the second secondary fuel passage 871 via a second secondary fuel line 872.
  • the second secondary fuel is led around a propellant gas outlet 818 in a plurality of turns 874, so that optionally the second secondary fuel can be preheated here by heat-emitting propellant gas.
  • water vapor may form in the area of these turns 874 from pressurized water.
  • the second secondary fuel passage 871 is surrounded by an outer heat-resistant wall 864, which in turn is surrounded by a pressure-resistant housing 866, thus substantially completely closing the combustion chamber 806 and the inner space 803.
  • an insulation 868 is provided around the pressure-resistant housing 866. It should be noted that the insulation is intended in particular to leave heat in the system in order to avoid energy losses. In principle, protection against overheating is achieved by using existing heat to increase the volume of the propellant gas.
  • the expansion machine 902 of FIG. 9 includes two expansion subassemblies 903. Each expansion subassembly 903 has a cylinder 904 and a piston 914 guided therein.
  • a propellant gas expansion space 928 is provided for charging with propellant gas to expand there and result in movement of the piston 914.
  • a compression space 925 is provided, which is used for compressing air use.
  • the two pistons 914 are mechanically fixed to one another via a piston rod 930.
  • the piston rod 930 has a toothing on two sides, with which it is in engagement with two sprockets 932.
  • the sprockets 932 change their direction of rotation depending on the direction of movement of the piston rod 930.
  • Via freewheels 934 an oscillating movement of the piston rod 930 is converted into a torque with only one direction of rotation at the wheel hubs 936 and thus the associated drive shafts 942.
  • a chain drive 940 is provided for a synchronization of the wheel hubs 936.
  • the two expansion sub-assemblies 903 are right and left expansion sub-assembly, wherein the terms right and left reference to the representation of FIG 9.
  • propellant gas is supplied to the propellant gas expansion chamber 928 via a filling valve 912 on the left side.
  • the propellant gas then expands in the propellant gas expansion space 928, thereby causing the left piston 914 to move to the right.
  • the propellant gas expansion space 928 thereby increases, whereby the compression space 925 decreases and leads to compression of air contained therein.
  • air was previously admitted by the air filling valve 962, which is now compressed.
  • the compressed air may be discharged from the compression space 925 via the air outlet valve 958 and supplied to a desired use, in particular, a propellant gas generating device as a secondary fuel or combustion air.
  • the movement described also leads to a movement of the Piston rod 930 to the right, which leads to a left turn of the upper ring gear 932 and a clockwise rotation of the lower ring gear 932.
  • the left turn of the upper sprocket 932 is converted to a left turn torque on the upper wheel hub 936.
  • Due to the freewheel 934 in the lower ring gear 932 the movement leads to no torque at the wheel hub 936. Rather, in this case, the lower ring gear 932 and the lower hub 936 rotate in opposite directions.
  • the expansion of propellant gas in the left propellant gas expansion space 928 also causes the right piston 914 to move to the right so that the right propellant gas expansion space 928 decreases.
  • the exhaust valve 908 is opened, so that propellant gas thereby leaves the right propellant gas expansion space 928.
  • This propellant gas optimally has atmospheric pressure, but at the same time still has a relatively elevated temperature to the environment.
  • the propellant gas flowing out of the outlet valve 908 is thus supplied to a heat exchanger 970.
  • heat of the propellant gas can be released to water, whereby the water can be heated and used as a further, in particular second secondary fuel and fed to a propellant gas generating device.
  • the two pistons 914 coupled via the piston rod 930 form a movable linear unit and these two coupled pistons 914 are altogether also referred to as free pistons.
  • the right exhaust valve may be closed prior to reaching the end position of this free piston so that a residual amount of propellant gas remains in the right propellant gas expansion chamber 928 forming a gas cushion.
  • a central component of the invention is a propellant gas reactor, the task of which is to generate a maximum propellant gas volume flow under high pressure while optimally utilizing the heat energy contained in the fuel in order to supply it to a downstream machine.
  • the adaptation to different performance states of the overall machine ie a combination of the propellant gas reactor with an expansion machine or the like, is effected by a corresponding change in the supplied fuel, combustion air and SKT quantities.
  • the maximization of the propellant gas volume flow should take place taking into account the temperature compatibility of the materials used at the outlet of the reactor - and at the inlet of the machine - by using compressed air as combustion air, secondary fuels (SKT) in the form of compressed air, water or water vapor.
  • compressed air combustion air
  • secondary fuels SHT
  • the propellant gas reactor consists of a heat-insulated, pressure-resistant outer shell. Centrally in the lower area, fuel and the combustion air necessary for combustion at elevated pressure are supplied to a chamber in which the combustion process can take place completely.
  • SKT's can be fed in the form of additional compressed air, water or water vapor and fed to the combustion gas as shown for an embodiment in Fig. 8.
  • the propellant gas thus produced leaves the reactor through an opening in the upper area and serves to drive a machine, in particular an expansion machine.
  • these SKTs are supplied in such a way that their volume flows protect the outer reactor wall from overheating.
  • the use of a high-temperature resistant lining of the combustion chamber is necessary.
  • FIG. 9 also illustrates that the propellant gas comes from a propellant gas generator 900, referred to as reactor for short becomes.
  • This fuel gas generating device 900 is supplied with fuel and combustion air, and a first secondary fuel SKT1, which can be supplied as compressed air through the compression space 925, and a second secondary fuel SKT2, which can be prepared and provided in the heat exchanger 970 as heated water or steam.
  • the heat engine 1000 of FIGS. 10 to 12 includes two propellant gas reactors 1005 coupled to an expander 1102.
  • a propellant gas is generated, which in each case via an outlet 1018 and an adjoining propellant gas supply 1019 can each be supplied to an expansion subassembly 1103.
  • the propellant gas can in principle be supplied via a filling valve 1112 to a propellant gas expansion chamber 1128.
  • the propellant may be vented via an exhaust valve 1108.
  • an outlet line 1109 is connected downstream of the outlet valve 1108.
  • Expansion of propellant in the propellant gas expansion space 1128 of each of the expansion subassemblies 1103 increases the corresponding propellant expansion space 1128 and moves a piston 1114 via a piston end wall 1122.
  • the two pistons 1114 are mechanically coupled via a piston rod 1130 and movement of the pistons 1114 and thus Piston rod 1130 leads to a conversion into a torque in the conversion mechanism 1144.
  • the operation of the conversion mechanism 1144 corresponds approximately to that described in connection with the expansion machine according to FIG.
  • the propellant gas reactors 1005 are operated with a fuel and combustion air.
  • the fuel is supplied by means of a fuel pump 1038 and a fuel valve 1026 for controlling the fuel supply.
  • the combustion air is provided as compressed air by the expansion engine 1102, the compressed air being provided in the area of the air outlet valves 1158 as described. This compressed air is also supplied to the propellant gas reactor 1005 as the first secondary fuel outside the combustor 1006 through the first secondary fuel supply 1050.
  • water vapor is supplied as the second secondary fuel at the second secondary fuel supplies 1070.
  • the second secondary fuel is initially provided by a water pump 1042 and water flow control valve 1030 with pressure.
  • an initial preheating takes place through corresponding line windings 1076 in the area of the propellant gas outlet line 1109, through which the propellant gas flows out of the propellant gas expansion chamber 1128.
  • Further heating of the water, in particular toward the water vapor then takes place in the case of further windings 1074 in the region of the propellant gas feed 1019, which adjoins the outlet 1018 of the propellant gas reactor 1005.
  • the thus heated, in particular water heated to steam is then supplied as second secondary fuel through the second secondary fuel feeds 1070 the propellant gas reactor 1005.
  • Figures 11 and 12 illustrate again - starting from Figure 10 - a movement of the linear unit, which is formed from the two pistons 1114 and the piston rod 1130, to the right as shown. This is also to illustrate the pressure distributions.
  • propellant gas is introduced into the propellant gas expansion space 1128 on the left side Service. From FIG. 10 via FIG. 11 to FIG. 12, this propellant gas now leads to an increase in volume of the left propellant gas expansion chamber 1128 and thus a decrease in the pressure of the propellant gas contained therein. At the same time in the left compression chamber 1125, an increase in pressure of the air contained.
  • propellant gas is expelled from the right propellant gas expansion space 1128, with the pressure of the propellant gas remaining substantially the same there, namely approximately equal to atmospheric pressure. Also, the pressure in the compression space 1125 in the right cylinder 1104 remains substantially constant, namely at about atmospheric pressure, as air flows in through the air filling valve 1162. After reaching the position shown in Figure 12, the process reverses and the linear unit will go to the left again.
  • FIGS. 10 to 12 a central measuring, control and control unit 1010 is shown in FIGS. 10 to 12.
  • This measurement, control and control unit 1010 which is referred to as MRS 1010 for short, is used to control both the propellant gas generating means, including the fuel pump 1038, the fuel valve 1026 and the water pump 1042 and the water control valve 1030, as well as to control the expansion machine , so in particular the valves.
  • the conversion mechanism 1144 has a controlled freewheel, which is also controlled by the central MRS 1010.
  • the central MRS 1010 may also be used to couple multiple heat engines according to FIGS. 10-12.
  • the MRS 1010 also takes over a synchronization control, so that the heat engines, in particular the expansion machines with the same frequency or based on the resulting torque with the same speed but shifted phase are operated.
  • a mechanical synchronization coupling can be avoided, whereby the operation of one and in particular a plurality of heat engines is flexible and in particular variable.
  • the heat engine 1300 of FIG. 13 comprises a propellant gas generating device 1301 with two propellant gas reactors 1305 and one Expansion engine 1302 with a conversion mechanism 1344.
  • This heat engine 1300 substantially corresponds to the heat engine according to Figures 6A and 6B, wherein additionally a compressor 1350 is provided and coupled via the conversion mechanism 1344 with the expansion machine 1302.
  • the compressor 1350 has two first compression spaces 1352 and two second compression spaces 1354.
  • Each second compression space 1354 is formed in a compression body, namely compression piston 1356, wherein the compression piston 1356 are mechanically fixedly coupled to each other via a rack portion 1358 and basically form a moving body 1360.
  • Each of the first compression spaces 1352 is formed in a cylinder shell 1362 by moving the respective compression piston 1356.
  • each first compression space 1352 forms a first compression stage and every second one
  • Compression space a second compression stage. According to the presentation of the
  • the compression piston 1356 moves to the left, thereby compressing air in the first left side compression space 1352, which has previously flowed through compressor inlet valves 1364. With this compression in the first compression space 1352 on the left side air flows with increasing
  • the second compression stage is performed according to the operating position in FIG.
  • Already compressed air is in the second compression chamber 1354 this right side and is further compressed by the leftward movement of the compressor piston 1356 by the second compression chamber 1354 conditioned by reduces the movement of the compressor piston 1356.
  • the air compressed in this second stage may pass through a compressor outlet valve 1368 into a compressor discharge area 1370 and eventually be sent from there for further use.
  • the moving body 1360 which consists of the two compression pistons 1356 and the rack portion 1358, is basically the only moving part, except for the movable elements of the valves.
  • the moving body 1360 thus moves relative to the cylinder jacket 1362 and the compressor outlet portion 1370.
  • the rack portion 1358 For generating the oscillating movement of the moving body 1360, it is coupled via the rack portion 1358 to the upper ring gear 1332 of the conversion mechanism 1344, the ring gear 1332 being driven by the piston rod 1330 of the expansion machine 1302 is moved.
  • the movement of the moving body 1360 of the compressor 1350 is opposite to the movement of the piston rod 1330 of the expanding machine 1302.
  • the compressed air generated by the compressor 1350 may be used in the propellant gas reactors 1305, for example, as combustion air or as a secondary fuel.
  • the conversion mechanism 1444 of Figure 14 has two sprockets 1432 which are rotatably mounted in a housing 1446. Between the two Sprockets 1432 is mounted a first toothed piston rod 1430 of a first expansion machine and is in engagement with both sprockets 1432. A second piston rod 1429 of a second expansion machine is engaged only with a ring gear 1432.
  • the piston rods 1429 and 1430 move in opposite directions and, as shown in Fig. 14, the first piston rod 1430 is shown in a leftward moved position and, accordingly, the second piston rod 1429 is shown in a rightward moved position.
  • the movement of the first piston rod 1430 is transmitted directly to the upper or lower ring gear 1432.
  • the movement of the second piston rod 1429 is transmitted directly to the lower sprocket 1432 and via the lower sprocket, the first piston rod 1430 indirectly to the upper sprocket 1432, said directions relate to the illustration of FIG 14.
  • the rotational movement of the sprockets 1432 is transmitted depending on the direction by the upper or lower ring gear 1432 in a torque.
  • the force and torque effects are illustrated in Figure 15, according to which the upper piston rod 1430 can exert a force F1 with changing direction and the second piston rod 1429 also exerts a force F2 with changing direction.
  • the first piston rod 1430 carries out a force F1 directed to the right-in relation to the illustration of FIG. 15, this is transmitted to the upper sprocket 1432 in a leftward torque M 1 which is transmitted further to the wheel hub 1436.
  • the second piston rod 1429 exerts a leftward force F1, which is transmitted to the lower ring gear 1432, from there to the first piston rod 1430 and from there to the upper ring gear 1432, where it leads to a left-facing torque M2 ,
  • the torques M1 and M2 add up.
  • the force F1 of the first piston rod 1430 is directed to the left, this is transmitted to the lower ring gear 1432 as a torque M1 directed to the left and from there to the wheel hub 1436.
  • the force F2 of the second piston rod 1429 is directed to the right and is directly on the lower Sprocket 1432 transmitted and leads there to a left-facing torque M2.
  • the torques M1 and M2 add up.
  • the wheel hubs 1436 are coupled via a chain drive 1440 and corresponding torque can be selectively removed at the upper and / or lower wheel hubs 1436. According to this embodiment, a coupling of two expansion machines with only one conversion mechanism can be achieved in a simple manner. It only needs a second guide for the second piston rod 1429 are provided.
  • the propellant gas reactor 1605 operates with a fuel and combustion air and three secondary fuels, namely, compressed air as the first secondary fuel SKT1, water vapor as the second secondary fuel SKT2, and water as the third secondary fuel.
  • a measurement, control and control unit 1610 referred to as MRS 1610 for short, controls the supply of said five substances.
  • a compressor 1636 generates compressed air and also has a compressed air tank for storing compressed air. The compressed air is supplied to the MRS 1610 where it is firstly provided as combustion air for combustion in the combustion chamber 1606 and secondarily supplied to the propellant gas reactor 1605 as secondary fuel SKT1.
  • the heating in the heat exchanger 1680 is carried out by propellant gas leaving the illustrated expansion machine 1602. After the propellant gas has given off heat to the water in the heat exchanger 1680, it leaves the heat exchanger 1680.
  • the combustor 1606 is disposed and surrounded by a heat-resistant wall 1660. Outside the heat-resistant wall 1660, the water flows from a central wall
  • the first and second secondary fuels SKT1 and SKT2 are directed by means of tubes 1669 through the center wall 1662, substantially transversely through the channel 1661 and through the heat-resistant wall 1660, to the interior 1603 of the propellant gas reactor 1605. Further to the outlet 1618 of the propellant gas reactor 1605, the water is first added to the propellant gas. Subsequently, as viewed in the flow direction of the propellant gas, a boundary wall 1617 is provided in the outlet 1618.
  • the propellant gas is supplied via corresponding lines of the expansion machine.
  • the third secondary fuel is supplied to the propellant gas reactor in a start-up phase.
  • the second secondary fuel is preferably supplied after the start-up phase and the supply of the third secondary fuel is thereby reduced.
  • FIG. 17 shows a cylinder head 1701 of an expansion machine.
  • a jacket tube 1702 is arranged, in turn, a cylinder 1703 is arranged.
  • a piston 1704 is movably guided.
  • a so-called upset piston 1741 is arranged, which is basically firmly connected to the piston 1704.
  • a chamber with lubricating oil or compression damping oil 1705 is arranged.
  • propellant gas flows through an inlet valve 1706 into the cylindrical space in which the piston 1704 moves and pushes the piston 1704 to the left, as shown in FIG.
  • the inlet valve 1706 is closed and an outlet valve 1707 is opened.
  • Propellant gas is then forced out of the outlet at the outlet valve 1707 by the piston 1704.
  • the exhaust valve 1707 may be closed before reaching the end position by the piston 1704, so that by the remaining propellant gas Damping cushion is formed, which cushion the piston 1704 while accelerating in the opposite direction.
  • an emergency compression chamber 1711 is provided into which the piston 1704 would then move. As soon as the piston with one end face has arrived at the beginning of the emergency compression chamber 1711, this leads to a forced closure of the channel 1709 of the inlet valve 1706 and the channel of the outlet valve 1707. The piston is then cushioned in the emergency compression chamber 1711.
  • the chamber is provided with the lubricating oil or compression damping oil 1705. Should the damping by the emergency compression chamber 1711 not be sufficient, then the compression piston 1741 can basically disengage from the movement of the remaining piston 1704 and continue to enter the chamber with the compression damping oil 1705 and be damped there.
  • a temperature equalization space is provided, in which optionally a thermal filling is provided, which is to achieve a temperature compensation along, ie in the longitudinal direction of the cylinder 1703, in particular a compensation of high temperatures in the region of the cylinder head 1701 in the opposite direction of the cylinder 1703.
  • the piston 1801 in FIG. 18 is provided with a compression piston 1802, which are firmly connected to one another via shear pins 1803.
  • an upsetting cylinder 1806 is arranged, into which the compression piston 1802 is basically partially inserted.
  • a seal is effected by means of the sealing ring 1804.
  • the compression piston 1802 thus moves together with the piston 1801.
  • the piston 1801 is guided in a cylinder, not shown, by means of the guide rings 1805.
  • lubricating oil is supplied to the compression space 1806 via a lubricating oil supply 1808. Via lubricating outlets 1809, the lubricating oil reaches the outside of the piston 1801 and can lubricate it against a cylinder in which the piston 1801 is guided.
  • the piston ring set 1807 is provided for this purpose.
  • the shear pins 1803 may break and the force from the upset piston 1802 can be damped by the lubricating oil in the compression space 1806, which in this case can be further pushed out by the Schmieraustritte 1809.
  • a cylinder tube 1902 In a cylinder tube 1902 propellant gas is guided into an interior 1901 or it can exert force there on a piston, not shown.
  • an annular gap 1903 with a thermal oil filling is provided in order to distribute or balance temperature along the cylinder tube 1902, in particular in the longitudinal direction.
  • the annular gap 1903 is limited by a jacket tube 1904.
  • An insulating material 1905 which in turn is accommodated in an outer tube 1906, is arranged around the jacket tube 1904. Only from the outer tube 1906 to the outside takes place a temperature output from the system out, which is to be expected on the outer tube 1906 with a temperature in the range of 30 0 C.
  • the foundation with thermal full insulation carries the reactor body, as well as its superstructures and isolates the heat radiation of the combustion chamber downwards.
  • the reactor body consists of a good heat-conducting material (copper, or similar) and is alternated with heated gas channels (pressureless) and propellant gas passages (pressurized) interspersed.
  • the drawing shows the course of the propellant or propellant gas flow in the right half section and the course of the hot gases in the left half section.
  • the intermediate frame made of highly thermally conductive material creates a cavity between the reactor body and the head and collection plate (items 2 and 4) in which themaschinesch effetsnetz (Item 17) and the connections of the propellant injection nozzles (Pos.18) find place. Further, the gap is used as Bankgasumlenkhunt and serves the additional preheating of the propellant before its injection into the reactor.
  • the header and collector plate forms the top of the reactor core and collects all of the reactor core fuel gas channels via the connecting tubes to the reactor core to one or more central working pressure lines (C1).
  • the head and collection plate has the necessary openings for the passage of the hot gases upwards.
  • the insulating cover forms the upper thermal termination of the reactor core and insulates it against the otherwise occurring Anlagenrometudeabhne upwards.
  • the insulating cover has the necessary openings for the conduction of the hot gases in the reactor cavity in which the pipe network for the condensate treatment (Pos.6) is located.
  • the condensate treatment plant consists of a pipe network which is filled to about 75% with condensate and largely extracts the residual energy of the hot gases leaving the reactor core in order to optimally preheat the condensate.
  • the condensate which is under approximately 60 bar pressure is supplied to the propellant injection nozzles (Item 18).
  • Possible overpressures are supplied via the control valve (Pos. 8) and the line C2 to the expansion part of the WWKM.
  • this valve In cooperation with WWKM's central power and machine control system and heat and pressure sensors, this valve primarily regulates the flow rate of the propellant, which creates the volume or pressure of the propellant gas in the reactor core, thus controlling the performance of the WWKM system becomes.
  • the valve for the condensate steam overpressure derives any overpressure via the pressure line C2 and leads this profitably to the expansion part of the WWKM system.
  • the accumulator pressure vessel ensures via its valves that even after the standstill and the cooling of the WWKM system there is enough propellant pressure to start the system again.
  • the working pressure measuring system is used to record the current working pressure and, in conjunction with the central machine control, to control and control the inlet valve (item 9 expansion system) of the expansion system.
  • the heat source is the energy supply of the WKM machine, it can be very different kind. Conceivable today, this heat source can be burned of gases, oils or coals, but also by nuclear energy.
  • the exhaust gas control system ensures a thermally and vacuum-regulated pipe or discharge and optimum utilization of the hot gases.
  • the condenser takes up the utilized pressureless propellant gas of the expansion system via the manifold D and cools them back only as far as possible, which in turn produces the warmest possible liquid propellant.
  • the condensate pump takes the condensed propellant coming from the condenser without pressure and delivers it to the pressurized condensate treatment plant.
  • the insulation housing insulates the entire reactor against heat loss to the outside.
  • the central power and machine control system monitors all machine states and controls and controls all machine and performance parameters to each other, as long as they are not controlled exclusively Drehwinkelsyncron.
  • the propellant conduit supplies the propellant via the control valve (item 7) to the propellant injector nozzles in the reactor core.
  • the propellant injectors atomize the propellant as fine as possible fog in the heated propellant gas channels, which almost explosively creates the propellant gas.
  • the machine foundation with the machine housing forms the outer frame of the machine and the connection to the cylinders.
  • the bearing blocks stand on the machine foundation and contain the bearings of the machine shafts.
  • the toothed segment wheels create the positive connection of the rack with the machine shafts or their freewheel on the respective return stroke of the machine.
  • the connecting rod connects both piston rods together and derives the forces generated in the Zahnsegmentiza.
  • the piston rods together with the pistons and their seals and the cylinders form the force-generating linear units.
  • the pistons contain the reversing valves and are part of the linear units.
  • the cylinders complete consist of the cylinder tubes in which the pistons run with their seals, as well as the cylinder heads with the exhaust valves and the cylinder feet with the piston rod seals and intake valves.
  • the intake valves are activated synchronously at the intake time and are influenced by the machine control at the time of closing.
  • the reversing valves are controlled synchronously. In the open state, they provide for the then released pressure equalization between the Wegschvo- lumen on the piston rod side and the cylinder head side, which due to the area difference of the powerful return stroke, in the connection of the propellant gas expansion and also resulting pressure reduction to approximately depressurized and the propellant gas recirculation due to the expansion , takes place.
  • the spring accumulator stores the kinetic energy resulting from the movement and the mass of the linear unit in the short term at the reversal of direction of the linear unit and leads them to this again after the change of direction.
  • the task of the piston rod seal and storage is to ensure that no propellant volume compensation takes place past them and the piston rods are stored smoothly.
  • the task of the piston seal and storage is to ensure that no propellant volume compensation takes place past them and the pistons are stored smoothly
  • the task of the output shaft seal is not to let the lubrication of the machine located in the housing interior lubricant to escape to the outside.
  • the intake valves always open (synchronously controlled) always exactly at the time of each change of direction of the respective direction of action to the outside, the working pressure-dependent closing time, however, is influenced by the central machine control (R. Pos. 16) beyond the following direction change, so always enough expansion pressure volume for the expansion stroke is available, whereby no vacuum losses can occur until the following direction change.
  • the WWKM does not need to be cooled at any point to protect against thermal damage.
  • the propellant gas reactor and the expansion engine (cylinder) should be well insulated against heat dissipation.
  • the WWKM develops a torque at each angle of rotation due to the constant lever arm (r). All engines have at about the time of their largest release of force as a result of the crankshaft torque generation lever arm length goes to 00 and as a result generates almost no torque. 4. In contrast to all types of engines, the WWKM develops power, torque and thus power in every angular position, it is a true one-stroke. Even as a double system, the WWKM is able to deliver only slightly fluctuating torque.
  • the WWKM technology is predestined for the production of very high power with high torques and low speeds.
  • the WWKM technology is used to drive always the same speed and power, then, if it has a positive influence on the efficiency, a conventional steam boiler can be used to generate propellant gas.
  • the reactor technology shown here allows a relatively fast speed or power change.
  • the WWKM technology will be predestined after its successfully completed development phase to be used as a prime mover for power plants, ships or locomotives. It will make a significant contribution to improving these facilities, especially with regard to economic and ecological operation.

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Abstract

L'invention concerne un dispositif de production de gaz propulseur destiné à produire un gaz propulseur sous pression en vue d'obtenir un travail mécanique. L'invention concerne en outre un procédé de production d'un gaz propulseur sous pression de manière à obtenir un travail mécanique en recourant à un dispositif de production de gaz propulseur doté d'un récipient sous pression de gaz propulseur, d'une chambre de combustion reliée au récipient sous pression de gaz propulseur et d'une amenée de propulseur secondaire destinée à introduire un propulseur secondaire dans le récipient sous pression de gaz propulseur. L'invention concerne en outre une machine de détente qui convertit l'énergie contenue dans le gaz propulseur sous pression en un déplacement mécanique, en particulier un déplacement de rotation, et qui présente un premier ensemble partiel de détente, ainsi qu'un procédé d'utilisation d'une machine de détente. L'invention concerne également une machine thermodynamique destinée à produire un déplacement mécanique en recourant à un combustible, un compresseur qui comprime un gaz de processus, en particulier de l'air, ainsi qu'un évaporateur qui produit de la vapeur d'eau à partir d'eau.
EP08801569.8A 2007-08-13 2008-08-13 Machine thermodynamique Active EP2179141B1 (fr)

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EP07114230 2007-08-13
EP08801569.8A EP2179141B1 (fr) 2007-08-13 2008-08-13 Machine thermodynamique
PCT/EP2008/006665 WO2009021729A2 (fr) 2007-08-13 2008-08-13 Machine thermodynamique

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EP2179141A2 true EP2179141A2 (fr) 2010-04-28
EP2179141B1 EP2179141B1 (fr) 2020-06-17

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CZ2010289A3 (cs) * 2010-04-14 2011-10-26 Cincura@Pavel Dvouválcový tepelný motor
FR2963805A1 (fr) * 2010-08-12 2012-02-17 Const Metalliques Et Mecaniques E C M M Et Dispositif de transmission d'effort pour un moteur a piston et moteur a piston comprenant un tel dispositif
CN102997239A (zh) * 2011-09-14 2013-03-27 杭鹰 氧化焰节能燃烧器
DE102012109679A1 (de) * 2012-10-11 2014-04-17 Anton Grassl Flügelzellenmaschine und Druckgaserzeugungsvorrichtung
DE102016119245A1 (de) 2016-10-10 2018-04-12 Harald Winkler Druckspeichervorrichtung und Speicherverfahren

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE904653C (de) * 1943-04-25 1954-04-29 Vorkauf Heinrich Verfahren zur Regelung der Fluessigkeitseinspeisung in umlaufenden Dampferzeugern
CH457973A (de) * 1966-05-06 1968-06-15 Sulzer Ag Gas-Dampfturbinenanlage
US3785146A (en) * 1972-05-01 1974-01-15 Gen Electric Self compensating flow divider for a gas turbine steam injection system
GB1470527A (en) * 1974-10-08 1977-04-14 Lang W Steam power plant
FR2474648A1 (fr) * 1980-01-25 1981-07-31 Nachbaur Georges Generateur de vapeur a haut rendement, applicable notamment a l'alimentation d'une turbine a vapeur, au chauffage et aux etuves
US4508064A (en) * 1981-11-12 1985-04-02 Katsuji Baba Internal combustion engine of hydrogen gas
DE8717848U1 (de) * 1987-03-25 1990-08-09 Lee, Sangchin, 7140 Ludwigsburg Zahntrieb zur Umsetzung einer Hin- und Herbewegung in die Drehbewegung einer Welle oder umgekehrt
US6112511A (en) * 1997-08-29 2000-09-05 Alliedsignal, Inc. Method and apparatus for water injection via primary jets
SE0400269L (sv) * 2003-08-01 2005-02-02 Michael Abrahamsson Förfarande och anordning för värmning medelst ett gasformigt medium.
DE102006021624B4 (de) * 2006-05-09 2011-06-22 Artmann, Michael, 93185 Vorrichtung und Verfahren zur Erzeugung von unter Druck stehendem Heißgas

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO2009021729A3 *

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WO2009021729A9 (fr) 2009-07-30
WO2009021729A2 (fr) 2009-02-19
EP2179141B1 (fr) 2020-06-17

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